GB1301282A - - Google Patents
Info
- Publication number
- GB1301282A GB1301282A GB1301282DA GB1301282A GB 1301282 A GB1301282 A GB 1301282A GB 1301282D A GB1301282D A GB 1301282DA GB 1301282 A GB1301282 A GB 1301282A
- Authority
- GB
- United Kingdom
- Prior art keywords
- bearing
- chamber
- supported
- shafts
- shaft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/20—Lubricating arrangements using lubrication pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
Abstract
1301282 Gas turbine engines; bearing systems DEFENCE SECRETARY OF STATE FOR 3 July 1970 [15 July 1969] 35681/69 Heading F1G A multi-shaft gas turbine engine comprises a first bearing chamber and a second bearing chamber each containing at least one bearing, there being ducting which communicates between both bearing chambers. The engine shown is a three-shaft by-pass gas turbine engine and comprises LP compressor or fan 7, IP compressor 4, HP compressor 1, combustion equipment 10, HP turbine 3, IP turbine 6 and LP turbine 9, the LP, IP and HP compressors and turbines being drivingly interconnected by shafts 8, 5 and 2 respectively. The shafts are supported by seven bearings A, B, C, D, E, F, G, the LP shaft being supported at its forward end by bearing A which is supported by stator structure 20, at an intermediate point by bearing B located between the LP and IP shafts 8, 5 and at its downstream end by bearing G which is supported by stator structure 21. The IP shaft 5 is supported at its forward end by bearing C which is supported by stator structure 22, and at its rearward end by bearing F which is supported stator structure 21. The HP shaft 2 is supported at its forward end in bearing D which is supported by stator structure 22 and at its rearward end by bearing E located between the HP and IP shafts. The bearings E, F, G are located in a rear bearing chamber 25 which is sealed by seals 26, 27, 28 through which pressurized air is allowed to leak into the chamber. The bearings B, C, D are located in an intermediate bearing chamber 30 which is sealed by seals 31, 32 through which pressurized air is allowed to leak into the chamber. The front bearing A is located in a front bearing chamber 35 which is sealed by seals 36, 37 through which pressurized air is allowed to leak into the chamber. The intermediate and rear bearing chambers 30 and 25 are interconnected by a tube 40 which is located between the HP and IP shafts 2, 5. The intermediate chamber 30 is connected to the front chamber 35 by passages 41 around the bearing B. Oil under pressure is supplied through line 54 and tube 45 located within the LP shaft 8 and passes to the bearings through metering orifices such as 46, 47 in the shafts 8, 5. The lubrication system is shown in Fig. 2 and comprises a main pump 52 which takes its suction from tank 51 and supplies oil through line 54 to the bearings A, B, C, D, E, F, G. Oil is withdrawn from the bearing chambers by scavenge pumps 65 and returned through line 67 and cooler 69 to the oil tank 51.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3568169 | 1969-07-15 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1301282A true GB1301282A (en) | 1972-12-29 |
Family
ID=10380402
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1301282D Expired GB1301282A (en) | 1969-07-15 | 1969-07-15 |
Country Status (2)
| Country | Link |
|---|---|
| DE (1) | DE2034188C3 (en) |
| GB (1) | GB1301282A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010031948A1 (en) * | 2008-09-22 | 2010-03-25 | Snecma | Method and system for lubricating a turbine engine |
| US8100646B2 (en) | 2008-05-16 | 2012-01-24 | Rolls-Royce Deutschland Ltd & Co Kg | Two-shaft engine for an aircraft gas turbine |
| EP2949884A1 (en) * | 2014-05-28 | 2015-12-02 | United Technologies Corporation | Scavenge filter system for a gas turbine engine |
| EP3783204A1 (en) | 2019-08-23 | 2021-02-24 | Raytheon Technologies Corporation | Squeeze film damper acoustic isolation and corresponding method |
| CN112627985A (en) * | 2020-12-02 | 2021-04-09 | 北京动力机械研究所 | Pressure balance mechanism of gas turbine engine lubricating system |
| CN113530680A (en) * | 2021-08-24 | 2021-10-22 | 中国航发湖南动力机械研究所 | Aviation turboshaft engine lubricating oil system and aviation turboshaft engine |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3826217A1 (en) * | 1988-08-02 | 1990-02-08 | Mtu Muenchen Gmbh | GAS TURBINE WITH A COMPRESSORED BEARING CHAMBER |
| CN116624271B (en) * | 2023-07-24 | 2023-09-15 | 成都中科翼能科技有限公司 | Bearing oil baffle assembly of gas turbine shaft |
-
1969
- 1969-07-15 GB GB1301282D patent/GB1301282A/en not_active Expired
-
1970
- 1970-07-09 DE DE19702034188 patent/DE2034188C3/en not_active Expired
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8100646B2 (en) | 2008-05-16 | 2012-01-24 | Rolls-Royce Deutschland Ltd & Co Kg | Two-shaft engine for an aircraft gas turbine |
| WO2010031948A1 (en) * | 2008-09-22 | 2010-03-25 | Snecma | Method and system for lubricating a turbine engine |
| FR2936273A1 (en) * | 2008-09-22 | 2010-03-26 | Snecma | METHOD AND SYSTEM FOR LUBRICATING A TURBOMACHINE |
| RU2498096C2 (en) * | 2008-09-22 | 2013-11-10 | Снекма | Method and system of gas-turbine engine lubrication |
| US8672095B2 (en) | 2008-09-22 | 2014-03-18 | Snecma | Method and system for lubricating a turbine engine |
| EP2949884A1 (en) * | 2014-05-28 | 2015-12-02 | United Technologies Corporation | Scavenge filter system for a gas turbine engine |
| US9849411B2 (en) | 2014-05-28 | 2017-12-26 | United Technologies Corporation | Scavenge filter system for a gas turbine engine |
| EP3783204A1 (en) | 2019-08-23 | 2021-02-24 | Raytheon Technologies Corporation | Squeeze film damper acoustic isolation and corresponding method |
| US11433322B2 (en) | 2019-08-23 | 2022-09-06 | Raytheon Technologies Corporation | Squeeze film damper acoustic isolation |
| CN112627985A (en) * | 2020-12-02 | 2021-04-09 | 北京动力机械研究所 | Pressure balance mechanism of gas turbine engine lubricating system |
| CN113530680A (en) * | 2021-08-24 | 2021-10-22 | 中国航发湖南动力机械研究所 | Aviation turboshaft engine lubricating oil system and aviation turboshaft engine |
Also Published As
| Publication number | Publication date |
|---|---|
| DE2034188B2 (en) | 1973-05-24 |
| DE2034188C3 (en) | 1973-12-06 |
| DE2034188A1 (en) | 1971-02-04 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed | ||
| PLE | Entries relating assignments, transmissions, licences in the register of patents | ||
| PCNP | Patent ceased through non-payment of renewal fee |